The majority of the text in this filewas extracted from the Juno Mission Plan Document, S. Stephens, 29 March2011.[JPL D-35556]


Mission Overview
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Juno launched on 5 August 2011. The spacecraft uses a deltaV-EGA trajectory consisting of a two part deep space maneuver on 30 August and 14 September 2012 followed by an Earth gravity assist on 9 October 2013 at an altitude of 559 km. Jupiter arrival is on 5 July 2016 using two 53.5-day capture orbits prior to commencing operations for a 1.3-(Earth) year-long prime mission comprising 32 high inclination, high eccentricity orbits of Jupiter. The orbit is polar (90 degree inclination) with a periapsis altitude of 4200-8000 km and a semi-major axis of 23.4 RJ (Jovian radius) giving an orbital period of 13.965 days. The primary science is acquired for approximately 6 hours centered on each periapsis although fields and particles data are acquired at low rates for the remaining apoapsis portionof each orbit.

Currently, 5 of the first 7 periapses are dedicated to microwave radiometry of Jupiter's deep atmosphere with most of the remaining orbits dedicated to gravity measurements to determine the structure of Jupiter's interior. All orbits will include fields and particles measurements of the planet's auroral regions. Juno is spin stabilized with a rotation rate of 2 rotations per minute (RPM). For the radiometry orbits the spin axis is precisely perpendicular to the orbit plane so that the radiometer fields of view pass through the nadir. For gravity passes, the spin axis is aligned to the Earth direction, allowing for Doppler measurements through the periapsis portion of the orbit. The orbit plane is initially very close toperpendicular to the Sun-Jupiter line and evolves over the 1.3-year mission.
Generally, data acquired during the periapsis passes are recorded and played back over the subsequent apoapsis portion of the orbit, although some datacan be downlinked during the gravity passes.

Juno's instrument complement includes Gravity Science using the X and Ka bands to determine the structure of Jupiter's interior; magnetometer investigation (MAG) to study the magnetic dynamo and interior of Jupiter as well as to explore the polar magnetosphere; and a microwave radiometer (MWR) experiment covering 6 wavelengths between 1.3 and 50 cm to perform deep atmospheric sounding and composition measurements. The instrument complement also includes a suite of fields and particle instruments to study the polar magnetosphere and Jupiter's aurora. This suite includes an energetic particle detector (JEDI), a Jovian auroral (plasma) distributions experiment (JADE), a radio and plasma wave instrument (Waves), an ultraviolet spectrometer (UVS), and a Jupiter infrared auroral mapping instrument (JIRAM). The JunoCam is a camera included for education and public outreach. While this is not a science instrument, we plan to capture the data and archive them in the PDS along with the other mission data. The MAG investigation consists of redundant flux gate magnetometers (FGM) and co-located advanced stellar compasses (ASC). The ASCs are provided by theDanish Technical University under an effort led by John Jorgenson.

Scott Bolton is the Juno Principal Investigator. The Science Team members responsible for the delivery and operation of the instruments are listed below:
Instrument Acronym Lead Co-I---------------------------------------------- -------- ---------
Gravity Science GRAV Folkner Magnetometer MAG Connerney Microwave Radiometer MWR Janssen Jupiter Energetic Particle Detector Instrument JEDI Mauk Jovian Auroral Distributions Experiment JADE McComas Radio and plasma wave instrument Waves Kurth Ultraviolet Imaging Spectrograph UVS Gladstone Jovian Infrared Auroral Mapper JIRAM Adriani Juno color, visible-light camera JUNOCAM Hansen

Mission Phases
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LAUNCH
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The Launch phase starts at L-40 min (Launch-40 min), and covers the interval from launch, through initial ground station acquisition, until the establishment of a pre-defined, stable, and slowly changing Sun- pointed attitude when cruise attitude control algorithms and ephemerides can be used. The end of the Launch phase is determined by post-launch health and safety assessments. The boundary is at L+3 days, after initial acquisition and after confirmation that the Flight System is safe and ina power-positive, thermally stable, and commandable attitude.

Target Name : N/A Mission Phase Start Time : 2011-08-05 (2011-217) Mission Phase Stop Time : 2011-08-08 (2011-220)

INNER CRUISE 1
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The Inner Cruise 1 phase lasts from post-Launch establishment of a pre-defined and stable Sun-pointed attitude when cruise attitude control algorithms and ephemerides can be used, until after initial spacecraft and instrument checkouts have been performed and the spacecraft has gotten far enough from the Sun to allow Earth-pointing instead of Sun-pointing. TCM 1 (the first planned trajectory correction maneuver) was deemed not necessary, hence, was not executed. The phase spans the interval from L+3to L+66 days.

Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2011-08-08 (2011-220) Mission Phase Stop Time : 2011-10-10 (2011-283)

INNER CRUISE 2
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The Inner Cruise 2 phase spans the period from L+66 days until L+663 days. The Deep Space Maneuvers (DSMs) occur during this phase, near aphelion of Juno's first orbit about the Sun, on the way to Earth Flyby and then Jupiter. There is increased DSN (Deep Space Network) coverage associated with the DSMs and a cleanup TCM. DSMs 1 and 2 occur on2012-08-30 and 2010-09-14.

Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2011-10-10 (2011-283) Mission Phase Stop Time : 2013-05-29 (2013-149)

INNER CRUISE 3
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The Inner Cruise 3 phase spans the interval from L+663 days to L+823 days. The duration of this cruise phase is 160 days. Featured in this phase is Earth Flyby (EFB), which gives Juno a gravity assist (providing 7.3 km/s of deltaV) on its way to Jupiter. It occurs as the spacecraft iscompleting one elliptical orbit around the Sun and includes perihelion.
Three TCMs were planned before EFB (the last of which was deemed not necessary) and one after EFB. There is increased DSN coverage associated with the 4 maneuvers and EFB. The Inner Cruise 3 phase is focused on performing the required maneuvers, as well as an integrated operationsexercise around Earth Flyby, subject to Flight System constraints.
Closest approach to Earth occurs on 2013-10-09 at 19:21 UTC.

Target Name : EARTH, SOLAR_SYSTEM Mission Phase Start Time : 2013-05-29 (2013-149) Mission Phase Stop Time : 2013-11-05 (2013-309)
Earth Closest Approach : 2013-10-09T19:21 (2013-282)

OUTER CRUISE
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The Outer Cruise phase lasts from L+823 days until the start of Jupiter Approach at Jupiter Orbit Insertion (JOI)-6 months (JOI-182 days or L+1614 days). The duration of this cruise phase is 791 days, which isover 2 years.

Target Name : SOLAR_SYSTEM Mission Phase Start Time : 2013-11-05 (2013-309) Mission Phase Stop Time : 2016-01-05 (2016-005)

JUPITER APPROACH
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The Jupiter Approach phase lasts the final 6 months of cruise before Jupiter Orbit Insertion and is an opportunity for final Flight System and instrument checkouts as well as science observations to start exercising the ground system and Flight System, although orbit insertion preparations limit instrument activities close to JOI. There are more frequent maneuvers approaching JOI, starting with a TCM at JOI-5 months, and correspondingly increasing DSN coverage. The 178-day Jupiter Approach phase is preceded by a 26-month Outer Cruise phase. Jupiter Approach starts 3 months after the project is fully staffed up in preparation for JOI and the 1.3 years of science orbits. The phase ends at JOI-4 days,which is the start of the JOI critical sequence.

Target Name: : JUPITER, SOLAR_SYSTEM Mission Phase Start Time : 2016-01-05 (2016-005) Mission Phase Stop Time : 2016-07-01 (2016-183)

JUPITER ORBIT INSERTION
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The JOI phase encompasses the JOI critical sequence. It begins 4 days before the start of the orbit insertion maneuver and ends 1 hour after the start. JOI, the second critical event of the mission, occurs at closest approach to Jupiter, and slows the spacecraft enough to let it be captured by Jupiter into a 53.5-day orbit and set up the geometry for the 14-day science orbits. A cleanup burn at JOI+8.6d during the Capture Orbits phase is required to clean up JOI maneuver execution errors. DSN coverageis continuous during the JOI phase.

Target Name : N/A Mission Phase Start Time : 2016-07-01 (2016-183) Mission Phase Stop Time : 2016-07-05 (2016-187)
Perijove 0 : 2016-07-05T02:47:38 (2016-187)

CAPTURE ORBITS
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The Capture Orbits phase starts at JOI+1h, after the end of the JOI critical sequence, and ends at PRM-5.25d, when instruments are off in preparation for the PRM maneuver. Between the two 53.5d capture orbits is PJ1 (Perijove 1), at which no maneuver is planned so it can be used as the first opportunity for science close to Jupiter and an opportunity to test the performance of the instruments in the Jupiter environment. A JOI cleanup maneuver at JOI+8.6d is required to clean up JOI maneuver execution errors, while additional maneuvers near the first apojove following JOI and at PJ1+14d ensure the timing of PJ1 and the large PRM burn at perijove of the following orbit. Solar conjunction occurs after apojove of the second capture orbit. DSN coverage remains continuous until the JOI+8.6d maneuver, then remains at elevated levels throughoutthe two capture orbits, and is continuous again around PJ1 and before PRM.
Instruments are on for most of the Capture Orbits, and there are routinecheckouts and science observations.

Target Name : JUPITER, SOLAR_SYSTEM Mission Phase Start Time : 2016-07-05 (2016-187) Mission Phase Stop Time : 2016-10-14 (2016-288)
Perijove 1 : 2016-08-27T12:51:20 (2016-240)

PERIOD REDUCTION MANEUVER
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The Period Reduction Maneuver phase starts at PRM-5.25d, and ends at PRM+50h, coinciding with the instrument keepout zone for the maneuver (no science observations are planned during this phase). The burn at PJ2 (Perijove 2) is designed to accomplish a decrease in the period and size of the orbit, thus the name Period Reduction Maneuver (PRM). PRM requires a cleanup maneuver in the following orbit to ensure proper timing for longitude coverage during the Science Orbits phase. DSN coverage iscontinuous from PRM-14d until PRM+5d.

Target Name : N/A Mission Phase Start Time : 2016-10-14 (2016-288) Mission Phase Stop Time : 2016-10-21 (2016-295)
Perijove 2 : 2016-10-19T18:11:07 (2016-293)

ORBITS 2-3
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The Orbits 2-3 phase starts at PRM+50h, after the end of the instrument keepout zone for the Period Reduction Maneuver, and near the beginning of the first 14-day orbit. It ends at PJ4-1d, which is the start of the first activity period (MWR AP4) in the Science Orbits. As such, the Orbits 2-3 phase includes most of the last half of Orbit 2 (PJ2 to AJ2) and all of Orbit 3 (AJ2 to AJ3). DSN coverage is continuous from the start of the phase until PRM+5d, and then follows a pattern similar to that used for the Science Orbits template. Instrument checkouts after PRM and scienceobservations during the rest of Orbit 2 and in Orbit 3 are planned.

Target Name : JUPITER Mission Phase Start Time : 2016-10-21 (2016-295) Mission Phase Stop Time : 2016-11-15 (2016-320)
Perijove 3 : 2016-11-02T17:52:29 (2016-307)

SCIENCE ORBITS
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The Science Orbits phase includes Orbit 4 through Orbit 36. Orbit N is defined from apojove (AJ) N-1 through apojove N, and includes perijove (PJ) N. Orbit numbering starts before the Science Orbits phase. JOI occurs at PJ0, so Orbit 0 lasts from PJ0 through AJ0 (including a JOI cleanup maneuver at JOI+8.6d). Orbit 1 includes PJ1, and runs from AJ0 through AJ1. Orbit 2 includes PJ2 (and PRM at PJ2), and runs from AJ1 through AJ2. Orbit 0, Orbit 1, and the first half of Orbit 2 together contain the two 53.5-day capture orbits. Orbit 3 includes PJ3 (and the PRM cleanup maneuver at PJ3+6h), and runs from AJ2 through AJ3. Early orbital science is baselined in Orbits 0, 1, 2, and 3, except for JOI and PRM keepout zones. Orbit 4 is the first science orbit. It includes PJ4 (and the first OTM at PJ4+7.5h), and runs from AJ3 through AJ4. The last science orbit is Orbit 36. It is bookkept as an extra science orbit, since the mission uses Orbits 4 through 35 to obtain 32 perijoves with MAG and other data that meet Level-1 baseline science requirements. Small (up to 8 m/s) orbit trim maneuvers (OTMs) are planned after each set of perijove science observations, at PJ+4h, PJ+6h, or PJ+7.5h in Orbits 4 through 35, to target the perijove longitude required for science observations in the next orbit. There is no need for an OTM after PJ36. Adeorbit maneuver (deterministic deltaV = 77 m/s) is planned near AJ36.

We distinguish activity periods from orbits. Orbits are used to refer to the mission design and navigation strategy (e.g., Nav data cutoffs, which occur near AJ orbit boundaries, and trajectory events), while activity periods are used to describe science and mission operations (e.g., sequences and data flow). An activity period (AP) runs from one PJ-1d to the next PJ-1d. Each AP is defined by the number of the PJ science pass it contains, and the type (MWR or GRAV). AP2 and AP3 are the first 14-day activity periods (differing slightly from science orbits activityperiods), and run from PJ2-1d through PJ3-1d and PJ3-1d through PJ4-1d.
AP3 is followed by the first activity period during the Science Orbits, AP4 (an MWR type), from PJ4-1d through PJ5-1d. The Science Orbits phase begins at the start of AP4, and continues through AP36, which ends early,at AJ36-1h, before the deorbit burn in the Deorbit phase.

Radiation accumulation increases substantially as the orbital line of apsides rotates and perijove latitude increases from 3 degrees at JOI to36 degrees at PJ36. There are currently no plans for an extended mission.

Target Name : JUPITER Mission Phase Start Time : 2016-11-15 (2016-320) Mission Phase Stop Time : 2018-02-13 (2018-044)
Perijove 4 : 2016-11-16T16:54:46 (2016-321) Perijove 5 : 2016-11-30T15:52:21 (2016-335) Perijove 6 : 2016-12-14T14:49:58 (2016-349) Perijove 7 : 2016-12-28T13:47:35 (2016-363) Perijove 8 : 2017-01-11T13:59:37 (2017-011) Perijove 9 : 2017-01-25T12:57:12 (2017-025) Perijove 10 : 2017-02-08T11:54:47 (2017-039) Perijove 11 : 2017-02-22T10:52:21 (2017-053) Perijove 12 : 2017-03-08T09:12:44 (2017-067) Perijove 13 : 2017-03-22T08:10:19 (2017-081) Perijove 14 : 2017-04-05T07:07:53 (2017-095) Perijove 15 : 2017-04-19T06:05:27 (2017-109) Perijove 16 : 2017-05-03T06:17:26 (2017-123) Perijove 17 : 2017-05-17T05:14:57 (2017-137) Perijove 18 : 2017-05-31T04:12:29 (2017-151) Perijove 19 : 2017-06-14T03:10:03 (2017-165) Perijove 20 : 2017-06-28T03:40:40 (2017-179) Perijove 21 : 2017-07-12T02:38:12 (2017-193) Perijove 22 : 2017-07-26T01:35:46 (2017-207) Perijove 23 : 2017-08-09T00:33:19 (2017-221) Perijove 24 : 2017-08-23T00:08:07 (2017-235) Perijove 25 : 2017-09-05T23:05:44 (2017-248) Perijove 26 : 2017-09-19T22:03:21 (2017-262) Perijove 27 : 2017-10-03T21:00:55 (2017-276) Perijove 28 : 2017-10-17T20:35:43 (2017-290) Perijove 29 : 2017-10-31T19:33:14 (2017-304) Perijove 30 : 2017-11-14T18:30:45 (2017-318) Perijove 31 : 2017-11-28T17:28:16 (2017-332) Perijove 32 : 2017-12-12T17:02:53 (2017-346) Perijove 33 : 2017-12-26T16:00:20 (2017-360) Perijove 34 : 2018-01-09T14:57:50 (2018-009) Perijove 35 : 2018-01-23T13:55:18 (2018-023) Perijove 36 : 2018-02-06T12:52:47 (2018-037)

DEORBIT
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The Deorbit phase occurs during the final perijove-to-perijove orbit of the mission. The 7-day phase starts several days after the Orbit 36 perijove science pass (part of the extra orbit) at AJ36-1h, before the start of the apojove deorbit maneuver (by which time we hope to have all or most of the PJ36 data on the ground). It continues through AJ36, and ends with Impact into Jupiter at PJ37. In order to meet planetary protection requirements and ensure that we do not impact Europa (as well as Ganymede and Callisto), the spacecraft performs a deorbit maneuver near apojove that reduces our orbital velocity and sends us to a perijove below Jupiter's cloud tops. The mean burn deltaV of 77 m/s is the largest maneuver of the mission after the 4 main engine maneuvers, and is planned to be performed on RCS (Reaction Control System) thrusters (deltaV to Earth angle, ELA ~ 70 degrees). The timing of the burn is not mission critical; a contingency delayed execution can occur several days around and following apojove if necessary. Impact into Jupiter marks End ofMission (EOM).

Target Name : JUPITER Mission Phase Start Time : 2018-02-13 (2018-044) Mission Phase Stop Time : 2018-02-20 (2018-051)
Perijove 37 : 2018-02-20T11:39:44 (2018-051)